EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 200,000 Max Cl/Cd: 94.31 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377-il-200000-n5.txt Download as CSV file: xf-e377-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 377 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1542 0.09598 0.09245 -0.0272 0.8219 0.0126
-7.250 -0.1452 0.09391 0.09023 -0.0277 0.7872 0.0130
-7.000 -0.1361 0.09202 0.08826 -0.0286 0.7688 0.0134
-6.750 -0.1238 0.09017 0.08634 -0.0304 0.7526 0.0137
-6.500 -0.1102 0.08836 0.08445 -0.0325 0.7369 0.0139
-6.250 -0.0954 0.08633 0.08234 -0.0348 0.7223 0.0140
-5.750 -0.0607 0.08204 0.07794 -0.0407 0.7008 0.0141
-5.500 -0.0405 0.07970 0.07555 -0.0442 0.6919 0.0142
-5.250 -0.0196 0.07720 0.07299 -0.0475 0.6822 0.0142
-5.000 0.0033 0.07462 0.07033 -0.0513 0.6735 0.0143
-4.750 0.0268 0.07193 0.06757 -0.0548 0.6650 0.0143
-4.500 0.0493 0.06853 0.06414 -0.0580 0.6575 0.0144
-4.250 0.0594 0.06418 0.05977 -0.0572 0.6503 0.0149
-4.000 0.0775 0.06157 0.05712 -0.0584 0.6430 0.0164
-3.750 0.1041 0.05918 0.05466 -0.0619 0.6359 0.0192
-3.500 0.1421 0.05704 0.05242 -0.0679 0.6290 0.0214
-3.250 0.1867 0.05518 0.05042 -0.0754 0.6222 0.0219
-3.000 0.2257 0.05277 0.04789 -0.0811 0.6157 0.0220
-2.750 0.2605 0.05010 0.04509 -0.0853 0.6099 0.0221
-2.500 0.2740 0.04584 0.04086 -0.0851 0.6039 0.0231
-2.250 0.3009 0.04361 0.03853 -0.0871 0.5985 0.0248
-2.000 0.3586 0.04285 0.03756 -0.0952 0.5920 0.0308
-1.750 0.3979 0.04068 0.03523 -0.0992 0.5865 0.0310
-1.500 0.4337 0.03837 0.03278 -0.1023 0.5813 0.0311
-1.250 0.4645 0.03498 0.02931 -0.1051 0.5757 0.0317
-1.000 0.4943 0.03276 0.02698 -0.1070 0.5709 0.0323
-0.500 0.5623 0.02867 0.02264 -0.1114 0.5605 0.0261
-0.250 0.6010 0.02701 0.02076 -0.1140 0.5559 0.0294
0.000 0.6358 0.02522 0.01882 -0.1160 0.5508 0.0280
0.250 0.6721 0.02338 0.01677 -0.1178 0.5459 0.0263
0.500 0.7094 0.02130 0.01439 -0.1197 0.5418 0.0249
0.750 0.7497 0.01825 0.01092 -0.1217 0.5371 0.0239
1.000 0.7872 0.01479 0.00664 -0.1232 0.5328 0.0242
1.250 0.8157 0.01414 0.00571 -0.1231 0.5285 0.0259
1.500 0.8437 0.01371 0.00511 -0.1229 0.5238 0.0289
1.750 0.8710 0.01358 0.00496 -0.1227 0.5187 0.0370
2.000 0.8984 0.01339 0.00468 -0.1224 0.5144 0.0509
2.250 0.9256 0.01343 0.00466 -0.1222 0.5099 0.0662
2.500 0.9525 0.01357 0.00479 -0.1219 0.5047 0.0806
2.750 0.9794 0.01364 0.00486 -0.1216 0.5004 0.0899
3.000 1.0062 0.01361 0.00479 -0.1213 0.4959 0.0957
3.250 1.0330 0.01363 0.00485 -0.1211 0.4907 0.1030
3.500 1.0601 0.01368 0.00488 -0.1208 0.4863 0.1120
3.750 1.0870 0.01377 0.00500 -0.1206 0.4816 0.1255
4.000 1.1137 0.01384 0.00515 -0.1203 0.4763 0.1400
4.250 1.1401 0.01394 0.00525 -0.1200 0.4717 0.1548
4.500 1.1666 0.01406 0.00542 -0.1197 0.4662 0.1742
4.750 1.1929 0.01417 0.00560 -0.1194 0.4602 0.1930
5.000 1.2191 0.01430 0.00580 -0.1191 0.4544 0.2165
5.250 1.2453 0.01442 0.00601 -0.1188 0.4472 0.2429
5.500 1.2712 0.01455 0.00620 -0.1184 0.4407 0.2811
5.750 1.2962 0.01432 0.00648 -0.1181 0.4330 0.6907
6.250 1.3508 0.01441 0.00694 -0.1180 0.4173 1.0000
6.500 1.3762 0.01463 0.00721 -0.1175 0.4084 1.0000
6.750 1.4011 0.01488 0.00747 -0.1171 0.3992 1.0000
7.000 1.4260 0.01512 0.00778 -0.1166 0.3883 1.0000
7.250 1.4506 0.01539 0.00811 -0.1161 0.3764 1.0000
7.500 1.4748 0.01569 0.00852 -0.1156 0.3630 1.0000
7.750 1.4986 0.01603 0.00891 -0.1150 0.3477 1.0000
8.000 1.5216 0.01645 0.00935 -0.1143 0.3297 1.0000
8.250 1.5437 0.01695 0.00986 -0.1136 0.3052 1.0000
8.500 1.5619 0.01787 0.01057 -0.1126 0.2597 1.0000
8.750 1.5760 0.01931 0.01167 -0.1113 0.2050 1.0000
9.000 1.5908 0.02064 0.01283 -0.1101 0.1679 1.0000
9.250 1.6024 0.02226 0.01427 -0.1086 0.1284 1.0000
9.500 1.6133 0.02382 0.01566 -0.1070 0.0983 1.0000
9.750 1.6215 0.02549 0.01718 -0.1051 0.0708 1.0000
10.000 1.6250 0.02742 0.01894 -0.1028 0.0449 1.0000
10.250 1.6248 0.02933 0.02076 -0.1001 0.0275 1.0000
10.500 1.6191 0.03146 0.02285 -0.0970 0.0153 1.0000
10.750 1.6138 0.03390 0.02533 -0.0947 0.0094 1.0000
11.000 1.6116 0.03639 0.02794 -0.0932 0.0076 1.0000
11.250 1.6106 0.03901 0.03070 -0.0922 0.0068 1.0000
11.500 1.6088 0.04192 0.03375 -0.0914 0.0062 1.0000
11.750 1.6057 0.04512 0.03710 -0.0909 0.0058 1.0000
12.000 1.6016 0.04856 0.04071 -0.0906 0.0055 1.0000
12.250 1.5975 0.05213 0.04450 -0.0905 0.0053 1.0000
12.500 1.5938 0.05572 0.04827 -0.0904 0.0052 1.0000
12.750 1.5888 0.05957 0.05230 -0.0906 0.0051 1.0000
13.000 1.5828 0.06364 0.05655 -0.0908 0.0050 1.0000
13.250 1.5762 0.06791 0.06100 -0.0913 0.0049 1.0000
13.500 1.5686 0.07238 0.06564 -0.0919 0.0049 1.0000
13.750 1.5609 0.07706 0.07049 -0.0927 0.0048 1.0000
14.000 1.5531 0.08192 0.07552 -0.0937 0.0047 1.0000
14.250 1.5455 0.08690 0.08067 -0.0949 0.0047 1.0000
14.500 1.5380 0.09200 0.08592 -0.0962 0.0046 1.0000
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